CN102722609B - Hingeless rotor blade model and layer pavement design method thereof - Google Patents
Hingeless rotor blade model and layer pavement design method thereof Download PDFInfo
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- CN102722609B CN102722609B CN201210168848.6A CN201210168848A CN102722609B CN 102722609 B CN102722609 B CN 102722609B CN 201210168848 A CN201210168848 A CN 201210168848A CN 102722609 B CN102722609 B CN 102722609B
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Abstract
The invention discloses a hingeless rotor blade model and a layer pavement design method thereof. The hingeless rotor blade model comprises a paddle hub, a vertical flexible beam, a horizontal flexible beam, a main paddle blade and a distance-variable hinge. According to the layer pavement design method, the number of composite material layers and layer pavement angles of the composite material layers are adopted as design variables. The layer pavement design method comprises the following steps: firstly, determining a design space, then analyzing the aeroelastic stability on every design situation in the design space so as to obtain functions of real parts of characteristic indexes of the aeroelastic stability of the paddle blade which are relative to design points, and solving the functions to obtain an optimal design scheme of the aeroelastic stability. The aeroelastic stability can be enhanced with the adoption of the layer pavement design method of a composite material rotor blade.
Description
Technical field
The invention belongs to helicopter structure design field, be specifically related to a kind of hingeless formula helicopter composite material rotor blade gas bullet Stability Model and laying method for designing thereof, can be applicable to the hingeless formula helicopter rotor blade of compound substance gas bullet stability Design.
Background technology
Rotor is one of most important parts of Helicopter System, is made up of the structure such as propeller hub and blade.Be mainly used to produce lift and operating physical force etc., determined flying quality, flight quality and the level of vibration of helicopter.The motion of rotor blade is extremely complicated, except itself is around the rotation of propeller hub, waves in addition, shimmy and displacement motion.In order to realize three kinds of motions, the level that is all provided with on the propeller hub of initial radial type lifting airscrew is cut with scissors, is vertically cut with scissors and pitch hinge.Also had afterwards in order to cancel vertical hinge and adopted universal joint propeller hub and seesaw type propeller hub, simplified rotor structure.Hingeless formula has further been cancelled level hinge, has only retained pitch hinge, and in multiple lifting airscrew systems, adopts.Although there is now bearingless rotor helicopter, hingeless formula helicopter remains extremely important a kind of rotor structure pattern.
The development of lifting airscrew technology has benefited from the application of compound substance, MBB company of the sixties in last century Germany is developed into the fiberglass blade that glass fibre strengthens and the carbon fibre reinforced composite adopting the seventies makes blade life improve 10 times from the 600h of wood materials, or even infinite life (more than 20000h).Compound substance not only can improve the rotor life-span, can also greatly reduce manufacturing cost, and therefore compound substance has become one of main material of helicopter present stage.
Gas bullet stability is one of major issue of helicopter, owing to having cancelled flapping hinge and lead lag hinge in hingeless formula lifting airscrew, has only retained pitch hinge, makes rotor blade dynamic response more complicated.Compound substance is widely adopted in hingeless formula lifting airscrew, has therefore occurred problem and phenomenon that some are new, and actual hingeless rotor blade is very complicated, therefore must set up reliable gas bullet Stability Model.Rotor blade is reduced to single flexible beam by traditional hingeless formula model, and by it to waving, shimmy and twisted coupling carries out approximate processing, is difficult to accurately obtain gas bullet stability.And compound material laying layer method can change rotor blade sports coupling relation, thereby change rotor gas bullet stability, therefore need to set up the hingeless formula composite rotor blade laying method for designing of considering gas bullet stability.
Summary of the invention
The present invention is directed to the gas bullet stability problem in the hingeless formula lifting airscrew of current compound substance system, proposed a kind of hingeless formula helicopter composite material rotor blade model and laying method for designing thereof.The hingeless formula composite rotor of the present invention Rotor Blade Model is made up of propeller hub, Vertical Flexible Beam, horizontal flexibility beam, main blade and pitch hinge.Vertical Flexible Beam is directly fixedly connected on propeller hub, and Vertical Flexible Beam and horizontal flexibility beam are rigidly connected, and horizontal flexibility beam is fixedly connected between main blade and Vertical Flexible Beam.Rotor blade model based on above-mentioned, the invention allows for hingeless formula composite rotor blade laying method for designing, and the method is carried out in accordance with the following steps:
The first step, according to the concrete structure static strength of helicopter rotor blade and fatigue resistance requirement, carries out preliminary laying design to Vertical Flexible Beam and horizontal flexibility beam, provides design space.
Second step, sets up the kinetics equation of rotor blade gas bullet stability.
To specifying blade design calculation of parameter two-dimensional section characteristic and one dimension beam, one dimension beam has comprised Vertical Flexible Beam, horizontal flexibility beam and main blade.One dimension beam adopts moderate deflection beam theory in calculating, and Aerodynamic Model adopts accurate Stable theory, and obtains the equation of motion by Hamilton principle.Discrete to main blade is several beam elements,, wherein Vertical Flexible Beam and horizontal flexibility beam are all discrete is a beam element, beam element has 2 end nodes, 3 interior nodes totally 20 degree of freedom; Paddle blade structure is carried out to finite element discretization, then can obtain the kinetic model of rotor blade in conjunction with the equation of motion;
The 3rd step, carries out gas bullet stability and solves.Eliminate item relevant with the time in kinetic model, and adopt Newton-Raphson method to obtain characteristic exponent, can judge the stability of rotor blade;
The 4th step, solves the next design point in design space, repeats second step～three step, until all design points of design space all complete calculating, can obtain the characteristic exponent under each rotor blade laying design conditions.
The 5th step, obtains corresponding n characteristic exponent that reflects gas bullet stability by n the design point of design space N, sets up the funtcional relationship of a gas bullet stability features index about design point, solves this function.The real part that meets characteristic exponent is less than 0, and hour has rotor system and have best gas bullet stability, can obtain thus the best corresponding rotor blade laying of gas bullet stability design proposal.
Hingeless formula lifting airscrew gas bullet Stability Model and laying method for designing thereof that the present invention proposes, owing to having considered in the face of cross section and the outer warpage of face, can obtain the gas bullet stability of hingeless rotor blade comparatively accurately.And the laying method for designing that adopts the present invention to propose can significantly improve the gas bullet stability of rotor blade.
Brief description of the drawings
Fig. 1 is hingeless rotor Rotor Blade Model schematic diagram provided by the invention;
Fig. 2 is hingeless rotor blade laying method for designing process flow diagram provided by the invention;
Fig. 3 be in embodiment gas bullet stability features index with laying angle changing trend diagram.
In figure:
1, propeller hub; 2, Vertical Flexible Beam; 3, horizontal flexibility beam;
4, main blade; 5, pitch hinge; 6, interior blade.
Embodiment
A kind of hingeless rotor Rotor Blade Model and the laying method for designing thereof that the present invention are proposed below in conjunction with drawings and Examples are elaborated.
As shown in Figure 1, first the present invention provides a kind of hingeless rotor Rotor Blade Model, and this model is made up of propeller hub 1, Vertical Flexible Beam 2, horizontal flexibility beam 3, main blade 4 and pitch hinge 5.Vertical Flexible Beam 2 and horizontal flexibility beam 3 are collectively referred to as interior blade 6, and Vertical Flexible Beam 2 is directly fixedly connected on propeller hub 1, and Vertical Flexible Beam 2 and horizontal flexibility beam 3 rigidly fix connection, and horizontal flexibility beam 3 is fixedly connected between main blade 4 and Vertical Flexible Beam 2.Horizontal flexibility beam 3 and Vertical Flexible Beam 2 have adopted composite structure, the laying method for designing that the present invention proposes, based on rotor blade model, carries out mainly for the composite structure laying design of Vertical Flexible Beam 2 and horizontal flexibility beam 3, as shown in Figure 2, concrete implementation step is as follows:
The first step, according to the concrete structure static strength of helicopter rotor blade and fatigue resistance requirement, carries out preliminary laying design to Vertical Flexible Beam 2 and horizontal flexibility beam 3, provides design space and is:
N＝(N
1N
2...N
n)
A wherein total n design point, N
i(i=1,2...n) is i design point, wherein each design point N
itwo design variable (t are comprised
iθ
i), each design point has comprised the thickness t of every one deck compound substance
iwith laying angle θ
i.
Second step, sets up the kinetics equation of rotor blade gas bullet stability.
Hingeless rotor blade is made up of two-dimensional section model and one dimension beam model, and wherein one dimension beam model has comprised Vertical Flexible Beam 2, horizontal flexibility beam 3 and main blade 4.Two-dimensional section is the two dimensional cross-section structure of rotor blade, can be obtained the stiffness matrix in cross section by two-dimensional section model, then obtain the equation of motion by one dimension beam model, section rigidity matrix is updated in the equation of motion, and carry out finite element discretization, the kinetics equation that can obtain rotor blade gas bullet stability, concrete steps are as follows:
(1) determine section rigidity matrix according to two-dimensional section characteristic model: arbitrfary point displacement on one dimension beam is divided into three degree of freedom in direction, i.e. displacement is s=[uvw]
t.Stress and strain has been considered in face and the outer two kinds of situations of face simultaneously.On cross section, the displacement of any point is also divided into two parts, i.e. s '=[vg]
t, wherein v is that on two-dimensional section, any point is with the displacement causing with reference to cross section in deformation process, g is with in face with reference to corresponding on cross section and the outer warpage displacement of face.Adopt Finite Element Method, can obtain cross sectional stiffness matrix K.
(2) obtain the equation of motion according to one dimension beam model: supposition propeller hub 1 is rigidity, main blade 4, horizontal flexibility beam 3 and Vertical Flexible Beam 2 are based on moderate deflection beam theory, considered that blade is bored in advance, plunderred in advance, the impact of pretwist and hinge biasing, composite material blade meets small strain hypothesis.Propeller hub fixed coordinate system, propeller hub rotating coordinate system, blade not deformation coordinate system and deformation coordinate are the relation that defines parameters, can carry out easily coordinate conversion, and above coordinate system is the conventional reference frame in helicopter design.Strain-displacement relation can be by moderate deflection beam theory, and considers to shear and reverse relevant warpage, uses order analysis theory to obtain.Stress-strain relation is supposed based on small strain, has adopted anisotropic composite material stress-strain relation, and Aerodynamic Model has adopted quasi-steady aerodynamic force, can obtain the equation of motion by Hamilton principle:
The nodal displacement vector that wherein q is beam element, M and C are respectively the quality and the damping matrix that have comprised aerodynamic force and inertia force influence, F is the external force that comprises all external force and nonlinear term effect, K is the cross sectional stiffness matrix that has comprised aerodynamic force, inertial force and structure influence, can be obtained by structure two dimensional cross-section property calculation.
(3) adopt Finite Element Method discrete to blade, wherein Vertical Flexible Beam and horizontal flexibility beam are all discrete is a beam element, and main blade is discrete is several beam elements, has all adopted and has had 2 end nodes, and 3 interior nodes amount to the beam element model of 20 degree of freedom.In conjunction with Finite Element Method and the equation of motion, set up thus the kinetic model of rotor blade.
The 3rd step, determines gas bullet stability.
First eliminate item relevant with the time in kinetic model, and adopt Newton-Raphson method to try to achieve characteristic exponent, concrete steps are the microvibration of hypothesis one dimension beam around equilibrium position, the equation of motion that substitution is set up by second step, can try to achieve the characteristic exponent of one dimension beam, if the real part of characteristic exponent is less than 0, represent that rotor system is stable, and the real part of this eigenwert more the bright rotor system of novel is more stable.
The 4th step, adopts next design point in the N of design space, repeats second step～three step, until all design points of design space all complete calculating, can obtain the characteristic exponent under each rotor blade laying design conditions.
The 5th step, has obtained corresponding n characteristic exponent that reflects gas bullet stability by n the design point of design space N, sets up the funtcional relationship of a gas bullet stability features index about design point, solves this function.The real part that meets characteristic exponent is less than 0, and hour has rotor system and have best gas bullet stability, can obtain thus the best corresponding rotor blade laying of gas bullet stability design proposal.
Embodiment
Adopt the method proposing to study composite rotor blade ply sequence, choose structure and the aerodynamic parameter of certain type lifting airscrew system, be specially the oar number of blade 4, blade radius is 5m, and blade chord length is 0.08m, rotating speed 40s
-1.In order to simplify calculating, select an angle in horizontal flexibility beam and Vertical Flexible Beam as design parameter here, the angle A in initial designs is 90 °, does not consider the impact of the compound substance number of plies.
The laying design proposal of table 1 flexible beam
| Horizontal flexibility beam | Vertical Flexible Beam | |
| Laying scheme | [A 3/(15°/-15°) 3/0° 2] | [A 3/(15°/-15°) 3/0° 2] |
Laying design proposal is expressed as that first to have laying angle be 3 layers, the compound substance of A, is then the double-decker of 3 layers 15 ° and-15 °, is finally 2 layers of 0 ° of laying.Wherein the span of A is between 0 ° to 90 °.Show to obtain funtcional relationship as shown in Figure 3 by calculating.By figure, when A=25 °, rotor blade has best gas bullet stability; And in the time of A=-50 °, the gas bullet stability of rotor blade is the poorest.Compare preliminary design scheme, the real part of the characteristic exponent of reflection gas bullet stability has reduced 1.98%, therefore adopts the method can improve the gas bullet stability of hingeless rotor blade.
Claims (2)
1. a hingeless rotor blade laying method for designing, it is characterized in that: described method is based on hingeless rotor Rotor Blade Model, described model is made up of propeller hub, Vertical Flexible Beam, horizontal flexibility beam, main blade and pitch hinge, Vertical Flexible Beam is directly fixedly connected on propeller hub, Vertical Flexible Beam and horizontal flexibility beam are rigidly connected, and horizontal flexibility beam is fixedly connected between main blade and Vertical Flexible Beam; Concrete laying method for designing comprises the steps:
The first step, according to the structural static strength of helicopter rotor blade and fatigue resistance requirement, carries out preliminary laying design to Vertical Flexible Beam and horizontal flexibility beam, provides design space; Described design space is:
N＝(N
1N
2...N
n)
A wherein total n design point, N
ibe i design point, wherein each design point N
itwo design variable (t are comprised
iθ
i), each design point has comprised the thickness t of every one deck compound substance
iwith laying angle θ
i, i=1,2...n;
Second step, set up the kinetics equation of rotor blade gas bullet stability: hingeless rotor blade is made up of two-dimensional section model and one dimension beam model, wherein one dimension beam model has comprised Vertical Flexible Beam, horizontal flexibility beam and main blade, two-dimensional section is the two dimensional cross-section structure of rotor blade, obtained the stiffness matrix in cross section by two-dimensional section model, then obtain the equation of motion by one dimension beam model, section rigidity matrix is updated in the equation of motion, and carry out finite element discretization, obtain the kinetics equation of rotor blade gas bullet stability;
The 3rd step, determines gas bullet stability;
The 4th step, solves the next design point in design space, repeats second step～three step, until the gas bullet stability of all design points of design space all completes calculating, obtains the characteristic exponent under each rotor blade laying design conditions;
The 5th step, obtains corresponding n characteristic exponent that reflects gas bullet stability by n the design point of design space N, sets up the funtcional relationship of a gas bullet stability features index about design point, solves this function; The real part that meets characteristic exponent is less than 0, and hour rotor system has best gas bullet stability, obtains thus the best corresponding rotor blade laying of gas bullet stability design proposal.
2. a kind of hingeless rotor blade laying method for designing according to claim 1, is characterized in that: the concrete steps of the described kinetics equation of setting up rotor blade gas bullet stability are:
(1) determine section rigidity matrix according to two-dimensional section characteristic model: arbitrfary point displacement on one dimension beam is divided into three degree of freedom in direction, i.e. displacement is s=[u v w]
t, stress and strain is considered in face and the outer two kinds of situations of face simultaneously; On cross section, the displacement of any point is also divided into two parts, i.e. s '=[v g]
t, wherein v is that on two-dimensional section, any point is with the displacement causing with reference to cross section in deformation process, g is with in face with reference to corresponding on cross section and the outer warpage displacement of face, adopts Finite Element Method, obtains cross sectional stiffness matrix K;
(2) obtain the equation of motion according to one dimension beam model: supposition propeller hub is rigidity, main blade, horizontal flexibility beam and Vertical Flexible Beam are based on moderate deflection beam theory, consider that blade is bored in advance, plunderred in advance, the impact of pretwist and hinge biasing, composite material blade meets small strain hypothesis, obtains the equation of motion by Hamilton principle:
The nodal displacement vector that wherein q is beam element, M and C are respectively the quality and the damping matrix that have comprised aerodynamic force and inertia force influence, F is the external force that comprises all external force and nonlinear term effect, and K is the cross sectional stiffness matrix that has comprised aerodynamic force, inertial force and structure influence;
(3) adopt Finite Element Method discrete to blade, wherein Vertical Flexible Beam and horizontal flexibility beam are all discrete is a beam element, and main blade is discrete is several beam elements, has all adopted and has had 2 end nodes, and 3 interior nodes amount to the beam element model of 20 degree of freedom; In conjunction with Finite Element Method and the equation of motion, set up thus the kinetic model of rotor blade.
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| CN105092191A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material propeller fatigue test system and method |
| CN108240304A (en) * | 2016-12-27 | 2018-07-03 | 北京金风科创风电设备有限公司 | Method and device for determining aeroelastic stability of wind turbine components |
| CN109693807B (en) * | 2018-12-28 | 2021-11-09 | 西北工业大学 | Design method of self-adaptive pneumatic variable-pitch propeller |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7630869B2 (en) * | 2003-05-27 | 2009-12-08 | University Of Washington | Method for predicting vibrational characteristics of rotating structures |
| CN101706833A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Design method for marine propeller made of carbon fiber composite material |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7630869B2 (en) * | 2003-05-27 | 2009-12-08 | University Of Washington | Method for predicting vibrational characteristics of rotating structures |
| CN101706833A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Design method for marine propeller made of carbon fiber composite material |
Non-Patent Citations (4)
| Title |
|---|
| "弹性耦合对直升机复合材料桨叶稳定性的影响";尹维龙、向锦武;《复合材料学报》;20060830;第23卷(第4期);第143-148页 * |
| "桨根柔性无铰旋翼桨叶气弹稳定性建模分析";石庆华、向锦武;《北京航空航天大学学报》;20070731;第33卷(第7期);第793-797页 * |
| 尹维龙、向锦武."弹性耦合对直升机复合材料桨叶稳定性的影响".《复合材料学报》.2006,第23卷(第4期),第143-148页. |
| 石庆华、向锦武."桨根柔性无铰旋翼桨叶气弹稳定性建模分析".《北京航空航天大学学报》.2007,第33卷(第7期),第793-797页. |
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